CN104401496A - Novel engine fixing structure - Google Patents
Novel engine fixing structure Download PDFInfo
- Publication number
- CN104401496A CN104401496A CN201410693282.8A CN201410693282A CN104401496A CN 104401496 A CN104401496 A CN 104401496A CN 201410693282 A CN201410693282 A CN 201410693282A CN 104401496 A CN104401496 A CN 104401496A
- Authority
- CN
- China
- Prior art keywords
- fuselage
- strut
- fixed
- left strut
- upper left
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000009434 installation Methods 0.000 claims description 15
- 229910000831 Steel Inorganic materials 0.000 claims description 12
- 239000010959 steel Substances 0.000 claims description 12
- 239000002828 fuel tank Substances 0.000 claims description 4
- 230000005484 gravity Effects 0.000 abstract description 3
- 230000003014 reinforcing effect Effects 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 238000010276 construction Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 244000145845 chattering Species 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
Landscapes
- Body Structure For Vehicles (AREA)
- Mutual Connection Of Rods And Tubes (AREA)
Abstract
The invention relates to a novel engine fixing structure, and belongs to the technical field of plane structure design. The novel engine fixing structure is characterized in that a plane body framework is connected with a mounting ring on an engine through three structures, namely, a top left supporting rod, a medium supporting rod and a bottom left supporting rod, wherein the top left supporting rod and the medium supporting rod are both connected with an top girder; the bottom left supporting rod is fixed to a lower girder; an oil tank bracket I and an oil tank bracket II are fixed to a lug plate I on the plane body framework through screws I, and the two brackets are fixed to an oil tank support on the engine through screws II. According to the novel engine fixing structure, the supporting rods and other structures are added to enable the plane body framework to be stably connected with the engine; meanwhile, the center of gravity of the engine can be further fixed by reinforcing the position of the top supporting rods; the flying performance of the plane can be further improved with the characteristics of structure simplicity, high reliability and handleability; agriculture aircrafts and other low-speed aircrafts apply; the novel engine fixing structure has the advantages of being small in manufacturing cost and high in feasibility.
Description
Technical field
The present invention relates to a kind of novel stationary engine structure, belong to technical field of aircraft structure design.
Background technology
Driving engine is the critical component of aircraft, is the unique power resources of aircraft.But in real process, the chattering of driving engine is obvious, after long-time use, its fastener likely loosens, and causes the phenomenons such as driving engine centre-of gravity shift.Once driving engine center-of-gravity position changes, just likely there is the situations such as rollover in taking off and landing of aircraft, this hides some dangers for regard to the flight safety for aircraft.
Summary of the invention
For solving the problem of driving engine unbalance, the object of the invention is to provide a kind of novel stationary engine structure to reinforce it.
To achieve these goals, the present invention adopts following technical scheme:
A kind of novel stationary engine structure, fuselage framework is connected with the installation ring on driving engine by upper left strut, middle strut, lower-left strut three kinds of structures, and wherein upper left strut, middle strut are all connected with upper crossbeam, and lower-left strut is then fixed on lower crossbeam;
Tank hanger I and tank hanger II are by screw I with on the auricle I be fixed on fuselage framework, and on the other hand, two supports are by the fixing fuel tank hanger on the engine of screw II.
The fuselage threaded connection I of upper left strut afterbody is connected with the upper bracket be welded on upper crossbeam by screw III, and I, the steel wire of upper left strut afterbody two nut clampings is fixed on fuselage.
The fuselage lower adaptor of lower-left strut afterbody is connected with the upper bracket be welded on lower crossbeam by screw IV.
Described upper left strut it comprise fuselage threaded connection I, installation ring upper left joint, nut II, upper left strut adjust bar and nut I, two auricles wherein on upper left strut adjust bar are then fixed on fuselage by steel wire II.
Described middle strut it comprise fuselage threaded connection II, middle strut adjust bar, nut IV, installation ring center tap and nut III, wherein fuselage threaded connection II is fixed by screws on fuselage.
Described lower-left strut it comprise fuselage lower adaptor, installation ring lower adaptor and steel pipe.
Beneficial effect of the present invention:
The present invention, by increasing the structures such as strut, makes fuselage framework can be connected with engine stabilizer, and the center of gravity of further stationary engine is carried out in the position simultaneously by reinforcing upper strut.The airworthiness that this invention structure is simple, good reliability, easy-to-operate characteristic can improve aircraft further, is applicable to the dopeies such as agricultural aircraft, has low cost of manufacture, feasibility advantages of higher.
Accompanying drawing explanation
Fig. 1 is engine assembly schematic diagram of the present invention;
Wherein: 1. driving engine, 2. upper left strut, strut 3., 4. lower-left strut, 5. fuselage framework, 6. go up crossbeam, 7. descends crossbeam.
Fig. 2 is A-A generalized section;
Wherein: 5. fuselage framework, 8. tank hanger I, 9. screw I, 10. auricle I, 11. tank hanger II, 12. fuel tank hangers, 13. screws II.
Fig. 3 is I face partial schematic diagram;
Wherein: 2. upper left strut, 14. screw III, 15. upper brackets, 16. steel wires I.
Fig. 4 is II face partial schematic diagram;
Wherein: 4. lower-left strut, 7. descend crossbeam, 17. lower brackets, 18. screws IV.
Fig. 5 is the constructional drawing of upper left strut 2;
Wherein: 19. fuselage threaded connection I, 20. auricle II, 21. steel wire II, 22. installation ring upper left joints, 23. nut II, 24. upper left strut adjusts bar, 25. nuts I.
Fig. 6 is the constructional drawing of middle strut 3;
Wherein: 26. fuselage threaded connections II, strut adjust bar in 27., 28. nut IV, 29. installation ring center taps, 30. nuts III;
Fig. 7 is the constructional drawing of lower-left strut 4;
Wherein: 31. fuselage lower adaptors, 32. installation ring lower adaptors, 33. steel pipes.
Detailed description of the invention
Describe the present invention below in conjunction with accompanying drawing:
The concrete fixing means of driving engine as shown in Figure 1, Figure 2, Figure 3 and Figure 4.
A kind of novel stationary engine structure, fuselage framework 5 is connected with the installation ring on driving engine 1 by upper left strut 2, middle strut 3, lower-left strut 4 three kinds of structures, wherein upper left strut 2, middle strut 3 are all connected with upper crossbeam 6, and lower-left strut 4 is then fixed on lower crossbeam 7;
Tank hanger I 8 and tank hanger II 11 are by screw I 9 with on the auricle I 10 be fixed on fuselage framework 5, and on the other hand, two supports are fixed on by screw II 13 on the fuel tank hanger 12 on driving engine 1.
The fuselage threaded connection I 19 of upper left strut 2 afterbody is connected with the upper bracket 15 be welded on upper crossbeam 6 by screw III 14, and I 16, the steel wire of upper left strut 2 afterbody two nut clampings is fixed on fuselage.
The fuselage lower adaptor 31 of lower-left strut 4 afterbody is connected with the upper bracket 17 be welded on lower crossbeam 7 by screw IV 18.
Fig. 5 display be the detail of construction of upper left strut 2, described upper left strut 2 it comprise fuselage threaded connection I 19, installation ring upper left joint 22, nut II 23, upper left strut adjust bar 24 and nut I 25, two auricles 20 wherein on upper left strut adjust bar 24 are fixed on fuselage by steel wire II 21.The position of further reinforcing upper left strut 2 thus increase the stability of engine location.
Fig. 6 display be the detail of construction of middle strut 3, described middle strut 3 it comprise fuselage threaded connection II 26, middle strut adjust bar 27, nut IV 28, installation ring center tap 29 and nut III 30, wherein fuselage threaded connection II 26 is fixed by screws on fuselage.
Fig. 7 display be the detail of construction of upper left strut 2, described lower-left strut 4 it comprise fuselage lower adaptor 31, installation ring lower adaptor 32 and steel pipe 33.
Claims (6)
1. a novel stationary engine structure, it is characterized in that: fuselage framework (5) is connected with the installation ring on driving engine (1) by upper left strut (2), middle strut (3), lower-left strut (4) three kinds of structures, wherein upper left strut (2), middle strut (3) are all connected with upper crossbeam (6), and lower-left strut (4) is then fixed on lower crossbeam (7);
Tank hanger I (8) and tank hanger II (11) by screw I (9) with on the auricle I (10) be fixed on fuselage framework (5), on the other hand, two supports are fixed on the fuel tank hanger (12) on driving engine (1) by screw II (13).
2. novel stationary engine structure according to claim 1, it is characterized in that: the fuselage threaded connection I (19) of upper left strut (2) afterbody is connected with the upper bracket (15) be welded on upper crossbeam (6) by screw III (14), the steel wire I (16) of upper left strut (2) afterbody two nut clampings is then fixed on fuselage.
3. novel stationary engine structure according to claim 1, is characterized in that: the fuselage lower adaptor (31) of lower-left strut (4) afterbody is connected with the upper bracket (17) be welded on lower crossbeam (7) by screw IV (18).
4. novel stationary engine structure according to claim 1, it is characterized in that: described upper left strut (2) it comprise fuselage threaded connection I (19), installation ring upper left joint (22), nut II (23), upper left strut adjust bar (24) and nut I (25), two auricles (20) wherein on upper left strut adjust bar (24) are then fixed on fuselage by steel wire II (21).
5. novel stationary engine structure according to claim 1, it is characterized in that: described middle strut (3) it comprise fuselage threaded connection II (26), middle strut adjust bar (27), nut IV (28), installation ring center tap (29) and nut III (30), wherein fuselage threaded connection II (26) is then fixed by screws on fuselage.
6. novel stationary engine structure according to claim 1, is characterized in that: described lower-left strut (4) it comprise fuselage lower adaptor (31), installation ring lower adaptor (32) and steel pipe (33).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410693282.8A CN104401496B (en) | 2014-11-27 | 2014-11-27 | A kind of stationary engine structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410693282.8A CN104401496B (en) | 2014-11-27 | 2014-11-27 | A kind of stationary engine structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104401496A true CN104401496A (en) | 2015-03-11 |
| CN104401496B CN104401496B (en) | 2016-09-21 |
Family
ID=52639189
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410693282.8A Active CN104401496B (en) | 2014-11-27 | 2014-11-27 | A kind of stationary engine structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104401496B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104890888A (en) * | 2015-04-24 | 2015-09-09 | 江西洪都航空工业集团有限责任公司 | Novel mounting and maintaining structure of oil tank |
| CN105329436A (en) * | 2015-11-17 | 2016-02-17 | 江西洪都航空工业集团有限责任公司 | Covering cap brace device |
| CN109592051A (en) * | 2018-12-03 | 2019-04-09 | 江西洪都航空工业集团有限责任公司 | A kind of engine installation structure |
| CN109720585A (en) * | 2017-10-30 | 2019-05-07 | 空中客车运营简化股份公司 | Aircraft |
| CN110844090A (en) * | 2019-10-11 | 2020-02-28 | 中国直升机设计研究所 | Supporting type mounting device of piston engine of helicopter |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1879632A (en) * | 1931-06-04 | 1932-09-27 | O'brien John Jeremiah | Engine release mechanism |
| US3028124A (en) * | 1958-05-16 | 1962-04-03 | Napier & Son Ltd | Mounting system of aircraft power plants |
| US3502287A (en) * | 1968-10-01 | 1970-03-24 | David B Lindsay | Aircraft engine mounting system |
| CN203612215U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Thrust pulling rod arranged between aero-engine and engine mounting structure |
| CN204279964U (en) * | 2014-11-27 | 2015-04-22 | 江西洪都航空工业集团有限责任公司 | A kind of novel stationary engine structure |
-
2014
- 2014-11-27 CN CN201410693282.8A patent/CN104401496B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1879632A (en) * | 1931-06-04 | 1932-09-27 | O'brien John Jeremiah | Engine release mechanism |
| US3028124A (en) * | 1958-05-16 | 1962-04-03 | Napier & Son Ltd | Mounting system of aircraft power plants |
| US3502287A (en) * | 1968-10-01 | 1970-03-24 | David B Lindsay | Aircraft engine mounting system |
| CN203612215U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Thrust pulling rod arranged between aero-engine and engine mounting structure |
| CN204279964U (en) * | 2014-11-27 | 2015-04-22 | 江西洪都航空工业集团有限责任公司 | A kind of novel stationary engine structure |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104890888A (en) * | 2015-04-24 | 2015-09-09 | 江西洪都航空工业集团有限责任公司 | Novel mounting and maintaining structure of oil tank |
| CN105329436A (en) * | 2015-11-17 | 2016-02-17 | 江西洪都航空工业集团有限责任公司 | Covering cap brace device |
| CN109720585A (en) * | 2017-10-30 | 2019-05-07 | 空中客车运营简化股份公司 | Aircraft |
| CN109720585B (en) * | 2017-10-30 | 2024-09-10 | 空中客车运营简化股份公司 | Aircraft with a plurality of aircraft body |
| CN109592051A (en) * | 2018-12-03 | 2019-04-09 | 江西洪都航空工业集团有限责任公司 | A kind of engine installation structure |
| CN110844090A (en) * | 2019-10-11 | 2020-02-28 | 中国直升机设计研究所 | Supporting type mounting device of piston engine of helicopter |
| CN110844090B (en) * | 2019-10-11 | 2022-11-22 | 中国直升机设计研究所 | Supporting type mounting device of piston engine of helicopter |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104401496B (en) | 2016-09-21 |
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Effective date of registration: 20170517 Address after: 330024 South flying point, hi tech Industrial Development Zone, Jiangxi, Nanchang Patentee after: Jiangxi Hongdu Aviation Industry Limited by Share Ltd Address before: 330000 Jiangxi city in Nanchang Province, the new bridge box 460 box 5001 Patentee before: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. |